elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Unsteady Wing-Pylon-Nacelle Interference in Transonic Flow

Dietz, Guido and Mai, Holger and Schröder, Andreas and Klein, Christian and Moreaux, N. and Leconte, P. (2008) Unsteady Wing-Pylon-Nacelle Interference in Transonic Flow. Journal of Aircraft, Vol. 45 (No. 3), pp. 934-944. American Institute of Aeronautics and Astronautics, Inc.. DOI: 10.2514/1.31363 ISSN 0021-8669

Full text not available from this repository.

Official URL: http://dx.doi.org/10.2514/1.31363

Abstract

The interference effects between an unswept supercritical airfoil model and an annular wing representing an engine nacelle were investigated. The investigation aims to better understand and predict the impact of the interence effects on the aeroelastic stability of large, modern transport aircraft at transonic speeds. The main objective was to identify potential aerodynamic instabilities in the interference region due to unsteady shock-wave/boundary-layer interactions. The applied model allows to roll and yaw th nacell relative to the model wing and to pitch the entire model. The aerodynamic response to these movements affects the aeroelastic stability of an aircraft and was also investigated here. The overlap between the wing and the nacelle, and the height of the pylon were designed by numerical simulations such as that locally supersonic velocities and flow separation in the interference region might occur. Two linear hydraulic jacks inside the model were used to perform prescribed yaw and roll movements of the nacelle including the pylon. The experiments were conducted up to Mach numbers of 0.84 in an adaptive solid-wall wind tunnel using a hydraulic driven pitch-oscillation setup. Boundary-layer transition was tripped on the wing as well as on the nacelle. The unsteady tests reveal a strong dependency of the aerodynamic response to the structural movement on the topology of the time-averaged flow field. During the static tests, an aerodynamic instability was detected for certain Mach-number/model-incidence combinations. In addition to the initial objectives, a simple countermeasurement was applied in the interference region and its effectiveness was demonstrated.

Item URL in elib:https://elib.dlr.de/50010/
Document Type:Article
Title:Unsteady Wing-Pylon-Nacelle Interference in Transonic Flow
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Dietz, GuidoUNSPECIFIEDUNSPECIFIED
Mai, HolgerUNSPECIFIEDUNSPECIFIED
Schröder, AndreasUNSPECIFIEDUNSPECIFIED
Klein, ChristianUNSPECIFIEDUNSPECIFIED
Moreaux, N.ONERAUNSPECIFIED
Leconte, P.ONERAUNSPECIFIED
Date:2008
Journal or Publication Title:Journal of Aircraft
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:Yes
Volume:Vol. 45
DOI :10.2514/1.31363
Page Range:pp. 934-944
Editors:
EditorsEmail
Weeks, Thomas, M.UNSPECIFIED
Publisher:American Institute of Aeronautics and Astronautics, Inc.
ISSN:0021-8669
Status:Published
Keywords:aerodynamics, aerodynamic derivatives, buffet
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Aeronautics
HGF - Program Themes:Aircraft Research (old)
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Flight Physics (old), L - Flexible Aircraft (old)
Location: Göttingen
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Experimental Methods
Institute of Aeroelasticity
Deposited By: Erdmann, Daniela
Deposited On:26 Jun 2008
Last Modified:27 Apr 2009 14:05

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.